lynx mission concept status - nasa · lynx mission concept status jessica a. gaskin (nasa msfc)...
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Lynx Mission Concept StatusJessica A. Gaskin (NASA MSFC)
Presented on behalf of the Lynx Team
❖ A symbol of great insight with the ability to see
through solid objects to reveal the true
nature of things.
❖ Much of the baryonic matter and the settings
of the most active energy release in the
Universe are visible primarily or exclusively in
the X-rays
S. Allen, Stanford
M. Bautz, MIT
W. N. Brandt, Penn State
J. Bregman, Michigan
M. Donahue, MSU
J. Gaskin, MSFC (Study Sci.)
Z. Haiman, Columbia
R. Hickox, Dartmouth
T. Jeltema, UCSC
J. Kollmeier, OCIW
A. Kravtsov, U. Chicago
L. Lopez, Ohio State
R. Osten, STScI
F. Paerels, Columbia
D. Pooley, Trinity
A. Ptak, GSFC
E. Quataert, Berkeley
C. Reynolds, UMD
D. Stern, JPL
Community STDT
F. Özel, Arizona (Co-Chair)
A. Vikhlinin, SAO (Co-Chair)
MSFC
https://ntrs.nasa.gov/search.jsp?R=20170007501 2020-01-11T23:51:30+00:00Z
Lynx and the Concept Study
The Lynx X-Ray Observatory Astro2020 Decadal Study Output:
1. A science case for the mission
2. A notional mission and observatory, including a
report on any tradeoff analyses
3. A design reference mission, including strawman
payload trade studies.
4. A technology assessment including: current status,
roadmap for maturation & resources
5. A cost assessment and listing of the top technical
risks to delivering the science capabilities
6. A top level schedule including a notional launch
date and top schedule risks.
• × 50 higher throughput while maintaining Chandra'sangular resolution.
• ×16 larger solid angle for sub-arcsec imaging
• ×800 higher survey speed at the Chandra Deep Field limit
• ×~1000 more power in grating spectroscopy
• High-resolution, spatially resolved spectroscopy on fine scales
The Dawn of Black HolesLynx will observe the birth of the first seed black holes at
redshift up to 10 and provide a census of the massive
black hole population in the local and distant universe,
follow their growth and assembly across cosmic time, and
measure the impact of their energy input on all scales. Of
interest to all astronomers working on the early universe,
galaxy formation, black holes.
Simulated 2x2 arcmin deep fields
JWST
‘First Galaxies’
4 Msec, 5″ resolution
Confusion Limited
4 Msec, Lynx
‘First Accretion Light’
The Invisible Drivers Behind Galaxy Formation and EvolutionThe assembly, growth, and the state of visible matter in the
cosmic structures is largely driven by violent processes that
produce energy that heats the gas in the CGM and IGM.
The exquisite spectral and angular resolution of Lynx will
make it a unique instrument for mapping the hot gas around
galaxies and in the Cosmic Web.
Facility Class Science
• First Black Holes and their Co-evolution with Galaxies
• Cycles of (Hot) Baryons in and out of Galaxies
• Feedback from Stars, Supernovae, and Black Holes
• Origin and Evolution of Stars and their Local Environments
• X-ray Counterparts of GW Events and Multi-Wavelength Phenomena
• Physics of Accretion and Compact Objects
Exploration Science with a Rich Community-
Driven Observer Program!
Lynx Optical AssemblyHigh-resolution X-ray Optical Assembly: 3 Viable Architectures – Trade Study
• Meta-Shell Si Optics (W. Zhang/GSFC)
• Adjustable Optics (P. Reid/SAO)
• Full Shell (K. Kilaru/USRA, G. Pareschi (Brera)C
XC
/D. B
erry
Up-select will be based on Science, Technical and
Programmatic criteria (TBF)
• Does the configuration Satisfy Science Requirements?
• Is there a feasible path for development?
• Are there existing X-ray measurements and/or analyses?
• Can it interface with the spacecraft and survive launch?
OWG will make a formal recommendation to STDT: 6/1/18STDT Finalizes their decision: 7/1/18
Lynx Optical Assembly
Angular resolution (on-axis) 0.5 arcsec” HPD (or better)
Effective area @ 1 keV 2 m2 (met with 3-m OD)
Off-axis PSF (grasp), A*(FOV for HPD < 1 arcsec) ≥ 2 m2 * 300 arcmin2
Wide FOV sub-arcsec Imaging 10 arcmin radius
Science Driven Requirements
Meta-Shell Approach
See Talks:
Component
Predicted Contribution to
HPD (“)
LynxRqrmnt
Status
Mirror segments
0.2 2.0
Alignment 0.1 1.5
Bonding 0.1 0.5
Thermal 0.2 0.2
Gravity release 0.1 0.1
Total 0.3 2.5
Segments Meta-shells Assembly
Single-Pair X-ray Test Module
Full Illumination4.5keV X-rays
3.8” HPD
(Zhang et al. NASA/GSFC)
Adjustable Shell Approach(Reid et al. SAO)
See Talks: ….
Design Parameters:
• Wolter-Schwarzschild
• 3 radial sets of modules (inner, middle, outer) ranging from 200 mm radius to 1500 mm radius
•292 shells (allowing for space between module rows
•42 modules (6 inner, 12 middle, 24 outer)
•~8200 segments (P and S combined)
•Azimuthal spans range from ~200 mm to ~400 mm
•Axial length 200 mm
•~ 107 piezoelectric adjuster cells in total
•Modeled performance”2.3 m2 @ 1 keVwith Ir coating
• Be, BeAl: low density, CTE; high modulus, yield strength
• Procure diamond-turned, heat treated, NiP coated shells (<100µm RMS)
• Diamond-turn and Zeeko polish• Differential deposition corrections
• Fused Silica: low density, low CTE• Procure high-quality quartz (or, hot slump)• Fine-grinding to 1.5µm OOR (P-V) + polish
to 5-6 nm RMS microroughness• Ion beam figuring corrections• Coating
Brera
MSFC
Full shell Optical Design
See Talks:
Lynx Optical Assembly
Deposition (MSFC, XRO)
Thermal Forming (GSFC, SAO)
Piezo stress (SAO/PSU)
Si Optics (GSFC)
Magnetic & deposition stress (NU)
Full shells(inner shells only)
Segments
Wedges
INTEGRATION
CORRECTION
FABRICATION
Segmented Assembly
Meta-Shell Assembly
Ion implant stress (MIT)
Ion beam
Ion beam
Implantedlayers
Top bearingN2
Glass Bottom Bearing
Air Bearing Slumping (MIT)Full Shell (Brera, MSFC, SAO)
Lynx Science Instruments
•X-Ray Grating Spectrometer (XGS)
•Instrument Design and Integration (On-going
@ MSFC ACO)
•High Definition X-ray Imager (HDXI)
•Instrument Design and Integration (On-going
@ MSFC ACO)
•X-ray Microcalorimeter Imaging
Spectrometer (XMIS)
•Instrument Design and Integration
(Completed 1st IDL @ GSFC)
See Talks:
Lynx Science Instruments
See Talks:
High Definition X-ray Imager (Notional)
Energy Range 0.2 – 10 keVQE > 90% (0.3-6 keV), QE > 10% (0.2-9 keV)
FOV 22’ x 22’ (4k x 4k pixels)
Pixel Size < 16 x 16 µm (≤ 0.33”)
Read Noise ≤ 4 e-
Energy Resolution 37 eV @ 0.3 keV, 120 eV @ 6 keV (FWHM)
Frame Rate > 100 frames/s (full frame)> 10000 frames/s (windowed region)
Radiation Tolerance 10 yrs at L2
X-ray Grating Spectrometer (Notional)
Effective Area ~4000 cm2 @ 0.3 keV (63% azimuthal coverage)
Resolving Power, R > 5,000
Energy Resolution < 5 eV (FWHM)
Count Rate Capability < 1 count/s/pixel
Array size 300 x 300 pixel array
Lynx X-ray Microcalorimeter (Notional
Pixel Size 1” (50 µm pixels for 10-m focal length)
FOV At least 5’ x 5’
Energy Resolution < 5 eV (FWHM)
Count Rate Capability < 1 count/s/pixel
Array size 300 x 300 pixel array
Mission Design
• Mission Lifecycle (Draft)
• Mission Design (MSFC ACO) + Trades
‒ Structures [Launch vehicle Trade]
‒ Thermal
‒ Propulsion
‒ Avionics [Comm Trade]
‒ GNC [Rapid response capability
Trade]
‒ Power
‒ Mechanisms [Moveable optics vs.
instrument table Trade]
‒ Environments [Orbit Trade]
Model-Based Systems Engineering Approach
focused on Concept of Operations
• WBS + dictionary• Stakeholder Viewpoints • System Block Diagrams• System Interface Diagrams (internal and external)• Use Diagrams
• Manufacturing• AI&T (major sub-systems)• Ground Operations• Launch Integration• Launch Operations (launch, deployment, T&CO)• Mission Timeline• Science Operations• Off-nominal Operations
• Functional Block Diagrams• System Requirements (Level 1 and 2)
Lynx X-ray Observatory – Notional Mission Lifecycle Schedule
Mission DesignO
rbit
L2
moon
Sun-Earth L2
TESS-type Orbit
BEST OPTIONS
Orbit Trades
•Launch Vehicle (Both)
•Delta-V (SE-L2)
•Thermal Environment (SE-L2)
•Eclipsing (SE-L2, just)
•Communications (TESS)
•Meteroid Environment (Both)
•Radiation Environment
(average/worst case – TBD)
•Serviceability (SE-L2)
•Disposal (TESS)
•Station Keeping (TESS)
•Disturbance Environment (Both)
Mission DesignPropulsion
SE-L2 TESS
Thrust (N) 66 66
Isp (s) 218 218
DV (m/s) 215.5 301.7
Propellant Mass (kg)
-with 15% Margin-
661.4 907.9
Propellant Volume (in3) 44,242 60,731
Propellant Tanks Needed 10 13
*Schematic shows the 10-tank configuration for the SE-L2 maneuver
Service Valve
Latch Valve
Pressure TransducerP
Flow Control Orifice
L
MRE-1.0MRE-15
Filter
• Monopropellant blowdown systemFuel = HydrazinePressurant = Gaseous Nitrogen
• Maneuver assumed: SE-L2DV required = 215.5 m/s
• Propellant mass for chosen maneuverHydrazine = 661.4 kg (includes 5% ACS tax and 10% margin)
• EnginesMain Engines: Northrop Grumman MRE-15
Thrust = 86 N at 27.6 bar, 66 N at 19.0 barIsp = 228 s at 19.0 bar
RCS/ACS Engines: Northrop Grumman MRE-1.0Thrust = 5.0 N at 27.6 bar, 3.4 N at 19.0 barIsp = 218 s at 19.0 bar
• Mass estimated using flight-qualified componentsRough estimate made for feedlines and mounts/fittings
Mission DesignMechanical
Integrated Science Instrument Module
Filter wheel attached to bottom of the cryostat – with sufficient clearance for door
Thrust tube design:
Internal strut design:
Mono-prop tanks
Internal contamination door & gratings mechanisms
Chandra Heritage Considered
X-ray Microcalorimeter
Filter wheel
Magnetic Broom
Optical Assembly
Outer Door/Sunshade
X-ray Microcalorimeter Designs
MBSE Output - Examples
Lynx WBS
Telescope Functional Diagram
Top-Level Organization
Telescope Block
Diagram
Thank You!
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